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FR2981733B1 - Module de chambre de combustion de turbomachine d'aeronef et procede de conception de celui-ci - Google Patents

Module de chambre de combustion de turbomachine d'aeronef et procede de conception de celui-ci

Info

Publication number
FR2981733B1
FR2981733B1 FR1159635A FR1159635A FR2981733B1 FR 2981733 B1 FR2981733 B1 FR 2981733B1 FR 1159635 A FR1159635 A FR 1159635A FR 1159635 A FR1159635 A FR 1159635A FR 2981733 B1 FR2981733 B1 FR 2981733B1
Authority
FR
France
Prior art keywords
designing
same
combustion chamber
chamber module
aircraft turbomachine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
FR1159635A
Other languages
English (en)
Other versions
FR2981733A1 (fr
Inventor
Sebastien Alain Christophe Bourgois
Jean-Francois Cabre
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Priority to FR1159635A priority Critical patent/FR2981733B1/fr
Priority to US14/353,966 priority patent/US9765970B2/en
Priority to GB1406632.8A priority patent/GB2511440B/en
Priority to PCT/FR2012/052442 priority patent/WO2013060985A1/fr
Priority to IN751MUN2014 priority patent/IN2014MN00751A/en
Publication of FR2981733A1 publication Critical patent/FR2981733A1/fr
Application granted granted Critical
Publication of FR2981733B1 publication Critical patent/FR2981733B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
FR1159635A 2011-10-25 2011-10-25 Module de chambre de combustion de turbomachine d'aeronef et procede de conception de celui-ci Active FR2981733B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR1159635A FR2981733B1 (fr) 2011-10-25 2011-10-25 Module de chambre de combustion de turbomachine d'aeronef et procede de conception de celui-ci
US14/353,966 US9765970B2 (en) 2011-10-25 2012-10-24 Aircraft turbomachine combustion chamber module and method for designing same
GB1406632.8A GB2511440B (en) 2011-10-25 2012-10-24 Aircraft turbomachine combustion chamber module having improved air distribution within the combustion chamber and method for designing same
PCT/FR2012/052442 WO2013060985A1 (fr) 2011-10-25 2012-10-24 Module de chambre de combustion de turbomachine d'aéronef et procédé de conception de celui-ci
IN751MUN2014 IN2014MN00751A (fr) 2011-10-25 2012-10-24

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1159635A FR2981733B1 (fr) 2011-10-25 2011-10-25 Module de chambre de combustion de turbomachine d'aeronef et procede de conception de celui-ci

Publications (2)

Publication Number Publication Date
FR2981733A1 FR2981733A1 (fr) 2013-04-26
FR2981733B1 true FR2981733B1 (fr) 2013-12-27

Family

ID=47221478

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1159635A Active FR2981733B1 (fr) 2011-10-25 2011-10-25 Module de chambre de combustion de turbomachine d'aeronef et procede de conception de celui-ci

Country Status (5)

Country Link
US (1) US9765970B2 (fr)
FR (1) FR2981733B1 (fr)
GB (1) GB2511440B (fr)
IN (1) IN2014MN00751A (fr)
WO (1) WO2013060985A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3009747B1 (fr) * 2013-08-19 2018-06-15 Snecma Chambre de combustion de turbomachine pourvue d'un passage d'entree d'air ameliore en aval d'un orifice de passage de bougie
WO2015102736A2 (fr) * 2013-10-24 2015-07-09 United Technologies Corporation Configuration de refroidissement d'un moteur de turbine à gaz pour chambre de combustion de moteur de turbine à gaz
FR3040765B1 (fr) 2015-09-09 2017-09-29 Snecma Element d'appui pour amortir des deplacements axiaux de traversee coulissante de systeme d'injection pour turbomachine
GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly
GB2548585B (en) * 2016-03-22 2020-05-27 Rolls Royce Plc A combustion chamber assembly
DE102016219424A1 (de) * 2016-10-06 2018-04-12 Rolls-Royce Deutschland Ltd & Co Kg Brennkammeranordnung einer Gasturbine sowie Fluggasturbine
FR3084447B1 (fr) * 2018-07-30 2020-07-31 Ifp Energies Now Chambre de combustion pour une turbine a gaz destinee a la production d'energie notamment d'energie electrique, comprenant des trous de dilution asymetriques dans un tube a flamme.

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6606861B2 (en) * 2001-02-26 2003-08-19 United Technologies Corporation Low emissions combustor for a gas turbine engine
US6976363B2 (en) * 2003-08-11 2005-12-20 General Electric Company Combustor dome assembly of a gas turbine engine having a contoured swirler
JP4653985B2 (ja) * 2004-09-02 2011-03-16 株式会社日立製作所 燃焼器とガスタービン燃焼器、及び空気を燃焼器に供給する方法
US7216485B2 (en) * 2004-09-03 2007-05-15 General Electric Company Adjusting airflow in turbine component by depositing overlay metallic coating
US7506512B2 (en) * 2005-06-07 2009-03-24 Honeywell International Inc. Advanced effusion cooling schemes for combustor domes
FR2892180B1 (fr) 2005-10-18 2008-02-01 Snecma Sa Amelioration des perfomances d'une chambre de combustion par multiperforation des parois
US7905094B2 (en) * 2007-09-28 2011-03-15 Honeywell International Inc. Combustor systems with liners having improved cooling hole patterns
US8127554B2 (en) * 2007-11-29 2012-03-06 Honeywell International Inc. Quench jet arrangement for annular rich-quench-lean gas turbine combustors

Also Published As

Publication number Publication date
GB2511440B (en) 2019-02-27
US9765970B2 (en) 2017-09-19
GB201406632D0 (en) 2014-05-28
GB2511440A (en) 2014-09-03
IN2014MN00751A (fr) 2015-07-03
WO2013060985A1 (fr) 2013-05-02
US20150285500A1 (en) 2015-10-08
FR2981733A1 (fr) 2013-04-26

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